Internal core profile for a turbine nozzle airfoil

ABSTRACT

An internal core profile for a second stage turbine nozzle airfoil of a gas turbine is provided. The turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

TECHNICAL FIELD

This application relates to airfoils for a gas turbine and more particularly to an internal core profile of an airfoil for a second stage turbine nozzle of a gas turbine.

BACKGROUND

Turbines are machines that obtain rotational force by impulsive or reaction force using a flow of a compressible fluid such as steam or gas, and include a steam turbine using steam, a gas turbine using hot combustion gas, and so on.

The gas turbine includes a compressor, a combustor, and a turbine. The compressor includes an air inlet into which air is introduced, and a plurality of compressor vanes and a plurality of compressor blades which are alternately arranged in a compressor housing. The introduced air is compressed by the compressor vanes and the compressor blades while passing through an inside of the compressor.

The combustor mixes fuel with compressed air supplied from the compressor and combusts the mixture of the fuel and the compressed air to generate high-temperature and high-pressure combustion gas.

The turbine includes a plurality of turbine vanes and a plurality of turbine blades which are alternately arranged in a turbine housing. In addition, a rotor is arranged to pass through centers of the compressor, the combustor, the turbine, and an exhaust chamber.

The rotor is rotatably supported at both ends thereof by bearings. A plurality of disks are fixed to the rotor, and a plurality of blades are connected to each of the disks while a drive shaft of a generator is connected to an end of the exhaust chamber.

In a gas turbine, many system requirements should be met at each stage of the gas turbine to meet design goals. The design goals may include overall improved efficiency and airfoil loading capability. For example, an internal core profile of turbine nozzle airfoil should achieve thermal and mechanical operating requirements for that particular stage. There is thus a desire for an improved airfoil core shape for a turbine nozzle for use in a turbine and the like. Further, internal cooling requirements should be optimized, necessitating a unique internal core airfoil profile to meet stage performance requirements enabling the turbine to operate in a safe, efficient and smooth manner.

SUMMARY

Aspects of one or more exemplary embodiments provide a unique internal core profile for an airfoil of a second stage turbine nozzle for a gas turbine capable of enhancing aeromechanics and reducing thermal and mechanical stresses.

Additional aspects will be set forth in part in the description which follows and, in part, will become apparent from the description, or may be learned by practice of the exemplary embodiments.

According to an aspect of an exemplary embodiment, there is provided a turbine nozzle including: an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. Here, the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

The airfoil core shape may lie within an envelope of +1-0.120 inches measured in a direction normal to any of the plurality of airfoil core profile sections.

The airfoil core may include a pressure side, a suction side, and a partition extending between the pressure side and the suction side to define a cooling path along which cooling fluid flows.

The airfoil core shape may include a core shape for a second stage turbine nozzle.

The turbine nozzle may further include a coating applied to the airfoil core shape, the coating having a thickness of less than or equal to 0.010 inches.

According to an aspect of another exemplary embodiment, there is provided a turbine including: a turbine nozzle extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. Here, the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

According to an aspect of another exemplary embodiment, there is provided a gas turbine including: a compressor configured to compress air; a combustor configured to mix compressed air supplied from the compressor with fuel for combustion; and a turbine including a plurality of turbine nozzles and a plurality of turbine blades rotated by combustion gas to generate power, wherein each of the turbine nozzles extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, and wherein the turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. Here, the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

BRIEF DESCRIPTION OF THE DRAWINGS

The above and other aspects will become more apparent from the following description of the exemplary embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a partially cutaway perspective view illustrating a gas turbine according to an exemplary embodiment;

FIG. 2 is a cross-sectional view illustrating a schematic structure of the gas turbine according to the exemplary embodiment;

FIG. 3 is a partial sectional view illustrating an internal structure of the gas turbine according to an exemplary embodiment;

FIG. 4 is a perspective view of a second stage turbine nozzle including an airfoil core according to an exemplary embodiment;

FIG. 5 is a front view of the second stage turbine nozzle including an airfoil core illustrated in FIG. 4;

FIG. 6 is a rear view of the second stage turbine nozzle including an airfoil core illustrated in FIG. 4;

FIG. 7 is a sectional view taken through the airfoil core of FIG. 6 according to an exemplary embodiment; and

FIG. 8 is an outer envelope of a nominal profile of the airfoil core according to an exemplary embodiment.

DETAILED DESCRIPTION

Various modifications and various embodiments will be described below in detail with reference to the accompanying drawings so that those skilled in the art can easily carry out the disclosure. It should be understood, however, that the various embodiments are not for limiting the scope of the disclosure to the specific embodiment, but they should be interpreted to include all modifications, equivalents, and alternatives of the embodiments included within the spirit and scope disclosed herein.

Hereinafter, exemplary embodiments will be described in detail with reference to the accompanying drawings. Throughout the disclosure, like reference numerals refer to like parts throughout the various figures and exemplary embodiments. In certain embodiments, a detailed description of functions and configurations well known in the art may be omitted to avoid obscuring appreciation of the disclosure by a person of ordinary skill in the art. For the same reason, some components may be exaggerated, omitted, or schematically illustrated in the accompanying drawings.

FIG. 1 is a partially cutaway perspective view illustrating a gas turbine according to an exemplary embodiment. FIG. 2 is a cross-sectional view illustrating a schematic structure of the gas turbine according to the exemplary embodiment.

Referring to FIGS. 1 and 2, the gas turbine 1000 may include a compressor 1100, a combustor 1200, and a turbine 1300. Based on a flow direction of gas (e.g., compressed air or combustion gas), the compressor 1100 is disposed at an upstream side of the gas turbine 1000, and the turbine 1300 is disposed at a downstream side of the gas turbine 1000. The combustor 1200 is disposed between the compressor 1100 and the turbine 1300.

The compressor 1100 includes compressor vanes 1120 and compressor rotors in a compressor housing. The turbine 1300 includes turbine vane 1320 and turbine rotors in a turbine housing. The compressor vanes 1120 and the compressor rotors are arranged in a multi-stage arrangement along the flow direction of compressed air. The turbine vanes 1320 and the turbine rotors are arranged in a multi-stage arrangement along the flow direction of combustion gas. The compressor 1100 is designed such that an internal space is gradually decreased in size from a front stage to a rear stage so that air drawn into the compressor 1100 can be compressed. On the contrary, the turbine 1300 is designed such that an internal space is gradually increased in size from a front stage to a rear stage so that combustion gas received from the combustor 1200 can expand.

A torque tube for transmitting a rotational torque generated by the turbine 1300 to the compressor 1100 is disposed between a compressor rotor that is located at the rearmost stage of the compressor 1100 and a turbine rotor that is located at the foremost stage of the turbine 1300. FIG. 2 illustrates a case in which the torque tube includes multiple torque tube disks arranged in a three-stage arrangement, but it is understood that this is only an example and other exemplary embodiments are not limited thereto. For example, the torque tube may include multiple torque tube disks arranged in an arrangement of equal to or greater than four stages or an arrangement of equal to or less than two stages.

Each of the compressor rotors includes a compressor rotor disk and a compressor blade 1110 fastened to the compressor disk. That is, the compressor 1100 includes a plurality of compressor rotor disks, and respective compressor rotor disks are coupled to each other by a tie rod to prevent axial separation in an axial direction. The compressor rotor disks are arranged in the axial direction with the tie rod extending through centers of the compressor disks. Adjacent compressor rotor disks are arranged such that opposing surfaces thereof are in tight contact with each other by being tightly fastened by the tie rod so that the adjacent compressor rotor disks cannot rotate relative to each other. Each of the compressor rotor disks has a plurality of compressor blades 1110 radially coupled to an outer circumferential surface thereof.

The compressor blades 1110 (or referred to as buckets) are radially coupled to an outer circumferential surface of each of the compressor rotor disks in a row. The compressor vanes 1120 (or referred to as nozzles) are provided on an inner circumferential surface of the compressor housing in an annular row in each stage, and rows of the compressor vanes 1120 are arranged between rows of the compressor blades 1110. While the compressor disks rotate along with a rotation of the tie rod, the compressor vanes 1120 fixed to the housing do not rotate. The compressor vanes 1120 guide the flow of compressed air moved from front-stage compressor blades to rear-stage compressor blades.

The tie rod is disposed to pass through centers of the plurality of compressor rotor disks and turbine rotor disks. One end of the tie rod is fastened to a compressor disk located at the foremost stage of the compressor 1100, and the other end thereof is fastened in the torque tube by a fastening nut.

It is understood that the tie rod is not limited to the example illustrated in FIG. 2, and may be changed or vary according to one or more other exemplary embodiments. For example, a single tie rod may be disposed to pass through the centers of the rotor disks, a plurality of tie rods may be arranged circumferentially, or a combination thereof may be used.

Further, a deswirler serving as a guide vane may be provided in the compressor 1100 to adjust an actual inflow angle of the fluid entering into an inlet of the combustor 1200 to a designed inflow angle.

The combustor 1200 mixes the introduced compressed air with fuel, burns a fuel-air mixture to produce high-temperature and high-pressure combustion gas with high energy, and increases the temperature of the combustion gas to a temperature at which the combustor and the turbine components are able to withstand an isobaric combustion process.

A plurality of combustors constituting the combustor 1200 of the gas turbine may be arranged in the housing in a form of a cell. The combustor 1200 may include a plurality of chambers 1210 and fuel nozzle modules 1220 arranged annually.

The high-temperature and high-pressure combustion gas supplied from the combustor 1200 flows into the turbine 1300 and expands while passing through the inside of the turbine 1300, thereby applying an impulsive force or reaction force to the turbine blades 1310 to generate a rotational torque. A portion of the rotational torque is transmitted to the compressor via the torque tube, and a remaining portion which is an excessive torque is used to drive a generator to produce power.

The turbine 1300 basically has a structure similar to the compressor 1100. That is, the turbine 1300 may include a plurality of turbine rotors similar to the compressor rotors, and each of the turbine rotor may include a turbine rotor disk and a turbine blade 1310 fastened to the turbine rotor disk. A plurality of turbine blades 1310 (or referred to as buckets) are radially disposed. A plurality of turbine vanes 1320 (or referred to as nozzles) are fixedly arranged on an inner circumferential surface of the turbine housing in an annular row in each stage, and rows of the turbine vanes 1320 are arranged between rows of the turbine blades 1310. The turbine vanes 1320 guide the flow direction of combustion gas passing through the turbine blades 1310.

FIG. 3 is a partial sectional view illustrating an internal structure of the gas turbine according to an exemplary embodiment. FIG. 4 is a perspective view of a second stage turbine nozzle including an airfoil core according to an exemplary embodiment. FIG. 5 is a front view of the second stage turbine nozzle including an airfoil core illustrated in FIG. 4. FIG. 6 is a rear view of the second stage turbine nozzle including an airfoil core illustrated in FIG. 4. FIG. 7 is a sectional view taken through the airfoil core of FIG. 6 according to an exemplary embodiment.

Referring to FIG. 3, the turbine 1300 may include a plurality of turbine stages employing a plurality of nozzles and a plurality of buckets. For example, the turbine may include a first stage having a first stage nozzle 1326 and a first stage bucket 1316, a second stage having a second stage nozzle 1320 and a second stage bucket 1310, and a third stage having a third stage nozzle 1332 and a third stage bucket 1322. Although FIG. 3 illustrates three turbine stages, this is only an example, and it is understood that any number of turbine stages may be used. Here, the second stage nozzle 1320 may include an airfoil core 1330 extending from a platform 1340 to an end wall 1342. For example, the turbine 1300 may include a plurality of second stage nozzles 1320 spaced, circumferentially, about a second stage nozzle assembly.

Referring to FIGS. 4 to 7, the turbine nozzle 1320 according to the exemplary embodiment includes a plurality of airfoil cores 1330 (i.e., internal airfoils) positioned circumferentially around the flow path of the gas turbine. Each airfoil core 1330 extends between a leading edge 1350 and a trailing edge 1352 in a stream wise direction and between a platform 1340 and an end wall 1342 in a spanwise direction. Each airfoil core 1330 is attached to the end wall 1342 of the airfoil core 1330. The airfoil cores 1330 can be integrally formed with the end wall 1342 through a casting process or the like or alternatively may be mechanically joined via welding or brazing.

Each airfoil core 1330 includes a pressure side 1360 and a suction side 1362. The pressure side 1360 and the suction side 1362 which are formed to extend from the leading edge 1350 to the trailing edge 1352 provide aerodynamic control of the flow of working fluid so as to optimize efficiency in the turbine 1300. That is, the turbine nozzle airfoil core 1330 extending from the platform 1340 to the end wall 1342 has an airfoil-shaped cross section having the leading edge 1350, the trailing edge 1352, the pressure side 1360, and the suction side 1362.

The airfoil core shape may be defined by a loci of points in space that meet stage design requirements. These points are unique and specific to the system. The list of X, Y, and Z coordinates for the airfoil core, which are included as Table 1, has been optimized for stage efficiency, aerodynamic efficiency, and thermal and mechanical life requirements. In one exemplary embodiment, the points may be arrived at by iteration between aerodynamic and mechanical design optimization. Accordingly, these are the only loci of points that allow the gas turbine to run at the most efficient, safe and smooth manner.

Referring to FIGS. 4 to 6, the airfoil core shape of the exemplary embodiment is defined by a unique set or loci of points in space that may be delineated. As shown in Table 1, the loci that defines the shape of the airfoil core may include a set of approximately 1,440 points with X, Y and Z coordinates. The X, Y and Z coordinates, which represent the airfoil core shape, are created in a coordinate system which is defined relative to the cold rotor centerline axis of the gas turbine (i.e., X coordinate axis). The origin of the coordinate system on the cold rotor centerline axis is defined as X=0.0, Y=0.0 and Z=0.0. For example, the coordinate system is set relative to the airfoil core and is fully defined by points A, B and C. Points A and B are both located 40.900 inches above the cold rotor centerline axis. Point A lies at an intersection of the airfoil core mean camber line and the leading-edge airfoil surface. Point B lies at an intersection of the airfoil core mean camber line and the trailing-edge airfoil surface. Point C is located 47.200 inches above the cold rotor centerline axis and lies at the intersection of the airfoil core mean camber line and the airfoil trailing-edge surface. Here, a coordinate system origin is located at point A. Points A and B define the positive X-axis. Points A, B and C define the positive X-Z plane. The Y-axis is then defined using the right-hand rule methodology. The coordinate values for the X, Y and Z coordinates are set forth in inches in Table 1, although other units of dimensions may be used if the values are appropriately converted.

The Cartesian coordinate system of X, Y and Z values given in Table 1 below defines the shape of the airfoil core according to an exemplary embodiment. More specifically, the shape of the airfoil core is defined by the cloud of points listed such that airfoil could be constructed by defining approximately smooth sheet surfaces through the listed points. As one of ordinary skill in the art will appreciate, Table 1 values are generated and shown to three decimal places for determining the profile of airfoil core. All of the 1,440 points represent a nominal cold or room temperature shape of the airfoil core. It will be appreciated that as the nozzle heats up in operation, mechanical loading and temperature will cause a change in X, Y and Z coordinates. Accordingly, values for the airfoil core shape given in Table 1 represent ambient, non-operating or non-hot conditions.

The coordinate values set forth in Table 1 below are for a cold condition of the turbine nozzle (e.g., non-rotating state and at room temperature). Further, the coordinate values set forth in Table 1 are for an uncoated nominal three-dimensional (3D) shape of the turbine nozzle. In some aspects, a coating (e.g., corrosion protective coating) may be applied to the turbine nozzle. The coating thickness may up to about 0.010 inches thick.

Further, the turbine nozzle 1320 may be fabricated using a variety of manufacturing techniques, such as forging, casting, milling, electro-chemical machining, electric-discharge machining, and the like. As such, the turbine nozzle may have a series of manufacturing tolerances for the position, profile, twist, and chord that can cause the turbine nozzle to vary from the nominal 3D shape defined by the coordinate values set forth in Table 1. This manufacturing tolerance may be, for example, +/−0.120 inches in a direction away from any of the coordinate values of Table 1 without departing from the scope of the subject matter described herein.

In addition to manufacturing tolerances affecting the overall size of the turbine nozzle, it is also possible to scale the airfoil core to a larger or smaller airfoil core size. In order to maintain the benefits of this 3D shape, in terms of stiffness and stress, it is necessary to scale the turbine nozzle uniformly in the X, Y, and Z directions.

The Table 1 values are generated and shown for determining the profile of the airfoil core. There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual profile of the airfoil core. Each section is joined smoothly with the other sections to form the complete airfoil core shape. It will therefore be appreciated that +/− typical manufacturing tolerances, i.e., +/− values, including any coating thicknesses, are additive to the X, Y and Z values given in Table 1 below.

TABLE 1 X Y Z Section 1 Point 1 7.608 −0.088 −1.422 Point 2 7.532 −0.206 −1.437 Point 3 7.608 −0.088 −1.422 Point 4 7.468 −0.104 −1.424 Point 5 7.328 −0.181 −1.434 Point 6 7.187 −0.257 −1.443 Point 7 7.045 −0.332 −1.453 Point 8 6.903 −0.404 −1.462 Point 9 6.760 −0.476 −1.471 Point 10 6.616 −0.546 −1.479 Point 11 6.471 −0.614 −1.488 Point 12 6.325 −0.680 −1.496 Point 13 6.179 −0.745 −1.504 Point 14 6.032 −0.808 −1.512 Point 15 5.884 −0.869 −1.520 Point 16 5.735 −0.928 −1.527 Point 17 5.585 −0.984 −1.534 Point 18 5.435 −1.039 −1.541 Point 19 5.283 −1.091 −1.548 Point 20 5.131 −1.140 −1.554 Point 21 4.978 −1.187 −1.560 Point 22 4.824 −1.231 −1.565 Point 23 4.669 −1.273 −1.571 Point 24 4.514 −1.311 −1.575 Point 25 4.358 −1.346 −1.580 Point 26 4.201 −1.378 −1.584 Point 27 4.043 −1.406 −1.587 Point 28 3.885 −1.431 −1.590 Point 29 3.726 −1.452 −1.593 Point 30 3.567 −1.468 −1.595 Point 31 3.407 −1.480 −1.597 Point 32 3.247 −1.487 −1.597 Point 33 3.087 −1.489 −1.598 Point 34 2.926 −1.485 −1.597 Point 35 2.767 −1.474 −1.596 Point 36 2.607 −1.457 −1.594 Point 37 2.449 −1.433 −1.591 Point 38 2.292 −1.400 −1.587 Point 39 2.138 −1.359 −1.581 Point 40 1.986 −1.308 −1.575 Point 41 1.838 −1.247 −1.567 Point 42 1.695 −1.175 −1.558 Point 43 1.558 −1.093 −1.548 Point 44 1.428 −1.000 −1.536 Point 45 1.305 −0.898 −1.524 Point 46 1.191 −0.787 −1.510 Point 47 1.083 −0.669 −1.495 Point 48 0.980 −0.547 −1.480 Point 49 0.880 −0.423 −1.464 Point 50 0.778 −0.300 −1.449 Point 51 0.666 −0.187 −1.434 Point 52 0.535 −0.096 −1.423 Point 53 0.382 −0.052 −1.417 Point 54 0.223 −0.063 −1.419 Point 55 0.090 −0.145 −1.429 Point 56 0.000 −0.276 −1.446 Point 57 −0.069 −0.419 −1.464 Point 58 −0.123 −0.569 −1.482 Point 59 −0.163 −0.723 −1.502 Point 60 −0.191 −0.879 −1.521 Point 61 −0.206 −1.037 −1.541 Point 62 −0.209 −1.196 −1.561 Point 63 −0.200 −1.355 −1.581 Point 64 −0.178 −1.512 −1.601 Point 65 −0.145 −1.668 −1.620 Point 66 −0.100 −1.820 −1.639 Point 67 −0.043 −1.969 −1.658 Point 68 0.024 −2.113 −1.676 Point 69 0.103 −2.252 −1.693 Point 70 0.192 −2.384 −1.710 Point 71 0.292 −2.508 −1.726 Point 72 0.402 −2.624 −1.740 Point 73 0.522 −2.729 −1.753 Point 74 0.651 −2.823 −1.765 Point 75 0.789 −2.903 −1.775 Point 76 0.934 −2.971 −1.784 Point 77 1.085 −3.024 −1.790 Point 78 1.240 −3.063 −1.795 Point 79 1.398 −3.089 −1.798 Point 80 1.558 −3.102 −1.800 Point 81 1.718 −3.103 −1.800 Point 82 1.878 −3.094 −1.799 Point 83 2.037 −3.075 −1.797 Point 84 2.195 −3.049 −1.793 Point 85 2.352 −3.015 −1.789 Point 86 2.507 −2.975 −1.784 Point 87 2.660 −2.930 −1.778 Point 88 2.812 −2.879 −1.772 Point 89 2.963 −2.825 −1.765 Point 90 3.112 −2.768 −1.758 Point 91 3.260 −2.707 −1.750 Point 92 3.407 −2.643 −1.742 Point 93 3.553 −2.577 −1.734 Point 94 3.698 −2.509 −1.726 Point 95 3.842 −2.439 −1.717 Point 96 3.985 −2.368 −1.708 Point 97 4.127 −2.294 −1.699 Point 98 4.268 −2.220 −1.689 Point 99 4.409 −2.144 −1.680 Point 100 4.550 −2.068 −1.670 Point 101 4.689 −1.990 −1.661 Point 102 4.829 −1.911 −1.651 Point 103 4.967 −1.832 −1.641 Point 104 5.106 −1.751 −1.631 Point 105 5.243 −1.670 −1.620 Point 106 5.381 −1.588 −1.610 Point 107 5.518 −1.506 −1.600 Point 108 5.654 −1.423 −1.589 Point 109 5.791 −1.340 −1.579 Point 110 5.927 −1.255 −1.568 Point 111 6.062 −1.171 −1.558 Point 112 6.198 −1.086 −1.547 Point 113 6.333 −1.000 −1.536 Point 114 6.467 −0.914 −1.526 Point 115 6.602 −0.827 −1.515 Point 116 6.736 −0.740 −1.504 Point 117 6.869 −0.652 −1.493 Point 118 7.003 −0.564 −1.482 Point 119 7.136 −0.475 −1.471 Point 120 7.268 −0.386 −1.459 Section 2 Point 1 7.777 −0.025 −0.406 Point 2 7.632 −0.040 −0.408 Point 3 7.486 −0.118 −0.418 Point 4 7.339 −0.195 −0.428 Point 5 7.192 −0.271 −0.437 Point 6 7.044 −0.344 −0.446 Point 7 6.895 −0.417 −0.455 Point 8 6.745 −0.488 −0.464 Point 9 6.594 −0.557 −0.473 Point 10 6.443 −0.624 −0.481 Point 11 6.290 −0.689 −0.490 Point 12 6.137 −0.752 −0.498 Point 13 5.983 −0.814 −0.505 Point 14 5.829 −0.873 −0.513 Point 15 5.673 −0.930 −0.520 Point 16 5.516 −0.985 −0.527 Point 17 5.359 −1.037 −0.533 Point 18 5.201 −1.087 −0.539 Point 19 5.042 −1.135 −0.545 Point 20 4.882 −1.179 −0.551 Point 21 4.722 −1.221 −0.556 Point 22 4.561 −1.259 −0.561 Point 23 4.399 −1.295 −0.566 Point 24 4.236 −1.327 −0.570 Point 25 4.072 −1.355 −0.573 Point 26 3.908 −1.380 −0.576 Point 27 3.744 −1.401 −0.579 Point 28 3.579 −1.418 −0.581 Point 29 3.413 −1.430 −0.582 Point 30 3.247 −1.437 −0.583 Point 31 3.082 −1.438 −0.584 Point 32 2.916 −1.434 −0.583 Point 33 2.750 −1.424 −0.582 Point 34 2.585 −1.406 −0.580 Point 35 2.421 −1.382 −0.576 Point 36 2.258 −1.349 −0.572 Point 37 2.098 −1.308 −0.567 Point 38 1.940 −1.257 −0.561 Point 39 1.786 −1.197 −0.553 Point 40 1.636 −1.126 −0.544 Point 41 1.492 −1.045 −0.534 Point 42 1.353 −0.954 −0.523 Point 43 1.222 −0.854 −0.510 Point 44 1.097 −0.745 −0.497 Point 45 0.978 −0.631 −0.482 Point 46 0.863 −0.512 −0.467 Point 47 0.749 −0.392 −0.452 Point 48 0.635 −0.273 −0.437 Point 49 0.512 −0.162 −0.423 Point 50 0.376 −0.068 −0.412 Point 51 0.221 −0.012 −0.405 Point 52 0.056 −0.014 −0.405 Point 53 −0.090 −0.088 −0.414 Point 54 −0.191 −0.217 −0.430 Point 55 −0.265 −0.364 −0.449 Point 56 −0.321 −0.519 −0.468 Point 57 −0.360 −0.679 −0.488 Point 58 −0.384 −0.842 −0.509 Point 59 −0.395 −1.006 −0.529 Point 60 −0.393 −1.171 −0.550 Point 61 −0.377 −1.335 −0.571 Point 62 −0.350 −1.497 −0.591 Point 63 −0.311 −1.657 −0.611 Point 64 −0.260 −1.814 −0.631 Point 65 −0.197 −1.966 −0.650 Point 66 −0.123 −2.113 −0.668 Point 67 −0.038 −2.255 −0.686 Point 68 0.058 −2.389 −0.703 Point 69 0.166 −2.514 −0.718 Point 70 0.283 −2.630 −0.733 Point 71 0.411 −2.735 −0.746 Point 72 0.548 −2.828 −0.758 Point 73 0.693 −2.908 −0.768 Point 74 0.845 −2.973 −0.776 Point 75 1.003 −3.025 −0.783 Point 76 1.164 −3.063 −0.787 Point 77 1.328 −3.088 −0.790 Point 78 1.493 −3.101 −0.792 Point 79 1.659 −3.102 −0.792 Point 80 1.825 −3.093 −0.791 Point 81 1.990 −3.076 −0.789 Point 82 2.154 −3.050 −0.786 Point 83 2.316 −3.017 −0.782 Point 84 2.478 −2.978 −0.777 Point 85 2.637 −2.934 −0.771 Point 86 2.796 −2.885 −0.765 Point 87 2.953 −2.831 −0.758 Point 88 3.108 −2.774 −0.751 Point 89 3.263 −2.714 −0.744 Point 90 3.416 −2.651 −0.736 Point 91 3.568 −2.585 −0.727 Point 92 3.719 −2.516 −0.719 Point 93 3.869 −2.446 −0.710 Point 94 4.018 −2.374 −0.701 Point 95 4.166 −2.300 −0.692 Point 96 4.313 −2.224 −0.682 Point 97 4.460 −2.147 −0.672 Point 98 4.606 −2.069 −0.663 Point 99 4.751 −1.989 −0.653 Point 100 4.896 −1.909 −0.643 Point 101 5.040 −1.827 −0.632 Point 102 5.184 −1.745 −0.622 Point 103 5.327 −1.661 −0.611 Point 104 5.469 −1.577 −0.601 Point 105 5.611 −1.492 −0.590 Point 106 5.753 −1.406 −0.580 Point 107 5.894 −1.320 −0.569 Point 108 6.035 −1.233 −0.558 Point 109 6.176 −1.145 −0.547 Point 110 6.316 −1.057 −0.536 Point 111 6.456 −0.968 −0.525 Point 112 6.595 −0.879 −0.513 Point 113 6.734 −0.789 −0.502 Point 114 6.873 −0.699 −0.491 Point 115 7.011 −0.608 −0.479 Point 116 7.149 −0.517 −0.468 Point 117 7.287 −0.425 −0.456 Point 118 7.424 −0.333 −0.445 Point 119 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Point 35 2.757 −1.385 0.431 Point 36 2.587 −1.367 0.433 Point 37 2.419 −1.341 0.437 Point 38 2.251 −1.306 0.441 Point 39 2.086 −1.264 0.446 Point 40 1.924 −1.212 0.453 Point 41 1.764 −1.151 0.460 Point 42 1.609 −1.081 0.469 Point 43 1.458 −1.001 0.479 Point 44 1.312 −0.913 0.490 Point 45 1.172 −0.817 0.502 Point 46 1.036 −0.714 0.515 Point 47 0.905 −0.605 0.529 Point 48 0.778 −0.492 0.543 Point 49 0.652 −0.377 0.557 Point 50 0.526 −0.263 0.572 Point 51 0.396 −0.154 0.585 Point 52 0.256 −0.058 0.597 Point 53 0.099 0.009 0.606 Point 54 −0.070 0.015 0.607 Point 55 −0.223 −0.056 0.598 Point 56 −0.338 −0.181 0.582 Point 57 −0.421 −0.329 0.563 Point 58 −0.480 −0.488 0.544 Point 59 −0.518 −0.653 0.523 Point 60 −0.541 −0.821 0.502 Point 61 −0.548 −0.990 0.481 Point 62 −0.541 −1.159 0.459 Point 63 −0.521 −1.327 0.438 Point 64 −0.489 −1.494 0.417 Point 65 −0.444 −1.657 0.397 Point 66 −0.387 −1.817 0.377 Point 67 −0.318 −1.972 0.357 Point 68 −0.238 −2.121 0.339 Point 69 −0.145 −2.263 0.321 Point 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6 7.351 −0.308 2.582 Point 7 7.188 −0.381 2.573 Point 8 7.025 −0.452 2.564 Point 9 6.860 −0.521 2.555 Point 10 6.695 −0.588 2.547 Point 11 6.529 −0.653 2.538 Point 12 6.362 −0.716 2.531 Point 13 6.194 −0.777 2.523 Point 14 6.026 −0.836 2.516 Point 15 5.857 −0.892 2.508 Point 16 5.686 −0.946 2.502 Point 17 5.516 −0.998 2.495 Point 18 5.344 −1.046 2.489 Point 19 5.171 −1.092 2.483 Point 20 4.998 −1.135 2.478 Point 21 4.824 −1.175 2.473 Point 22 4.650 −1.212 2.468 Point 23 4.474 −1.246 2.464 Point 24 4.298 −1.275 2.460 Point 25 4.121 −1.301 2.457 Point 26 3.944 −1.323 2.454 Point 27 3.767 −1.341 2.452 Point 28 3.588 −1.354 2.451 Point 29 3.410 −1.362 2.450 Point 30 3.232 −1.366 2.449 Point 31 3.053 −1.363 2.449 Point 32 2.875 −1.355 2.450 Point 33 2.697 −1.340 2.452 Point 34 2.519 −1.319 2.455 Point 35 2.343 −1.292 2.458 Point 36 2.168 −1.256 2.463 Point 37 1.995 −1.214 2.468 Point 38 1.823 −1.164 2.474 Point 39 1.655 −1.105 2.482 Point 40 1.489 −1.040 2.490 Point 41 1.326 −0.966 2.499 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112 6.860 −0.885 2.509 Point 113 7.010 −0.790 2.521 Point 114 7.161 −0.695 2.533 Point 115 7.311 −0.599 2.545 Point 116 7.461 −0.503 2.557 Point 117 7.611 −0.407 2.569 Point 118 7.761 −0.311 2.581 Point 119 7.911 −0.215 2.593 Point 120 8.061 −0.119 2.606 Section 6 Point 1 8.252 0.006 3.629 Point 2 8.158 −0.125 3.613 Point 3 8.252 0.006 3.629 Point 4 8.092 −0.006 3.627 Point 5 7.928 −0.086 3.617 Point 6 7.763 −0.164 3.608 Point 7 7.597 −0.241 3.598 Point 8 7.430 −0.316 3.589 Point 9 7.263 −0.389 3.579 Point 10 7.095 −0.460 3.571 Point 11 6.925 −0.529 3.562 Point 12 6.756 −0.596 3.553 Point 13 6.585 −0.661 3.545 Point 14 6.413 −0.724 3.537 Point 15 6.241 −0.785 3.530 Point 16 6.068 −0.844 3.522 Point 17 5.894 −0.900 3.515 Point 18 5.719 −0.954 3.509 Point 19 5.544 −1.005 3.502 Point 20 5.368 −1.053 3.496 Point 21 5.190 −1.099 3.490 Point 22 5.013 −1.141 3.485 Point 23 4.834 −1.181 3.480 Point 24 4.655 −1.217 3.476 Point 25 4.475 −1.249 3.472 Point 26 4.294 −1.278 3.468 Point 27 4.113 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Point 98 4.405 −2.379 3.330 Point 99 4.568 −2.298 3.340 Point 100 4.730 −2.214 3.351 Point 101 4.892 −2.129 3.361 Point 102 5.052 −2.042 3.372 Point 103 5.212 −1.953 3.383 Point 104 5.371 −1.863 3.395 Point 105 5.529 −1.772 3.406 Point 106 5.687 −1.680 3.418 Point 107 5.843 −1.587 3.429 Point 108 6.000 −1.492 3.441 Point 109 6.156 −1.397 3.453 Point 110 6.311 −1.302 3.465 Point 111 6.466 −1.205 3.477 Point 112 6.620 −1.108 3.489 Point 113 6.775 −1.010 3.501 Point 114 6.929 −0.912 3.514 Point 115 7.082 −0.814 3.526 Point 116 7.236 −0.715 3.538 Point 117 7.389 −0.617 3.551 Point 118 7.543 −0.518 3.563 Point 119 7.696 −0.419 3.576 Point 120 7.849 −0.320 3.588 Section 7 Point 1 8.349 0.000 4.636 Point 2 8.250 −0.131 4.620 Point 3 8.349 0.000 4.636 Point 4 8.185 −0.010 4.635 Point 5 8.016 −0.090 4.625 Point 6 7.846 −0.169 4.615 Point 7 7.675 −0.246 4.605 Point 8 7.504 −0.321 4.596 Point 9 7.332 −0.394 4.587 Point 10 7.159 −0.466 4.578 Point 11 6.986 −0.536 4.569 Point 12 6.811 −0.604 4.560 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8.323 Point 96 4.331 −2.658 8.334 Point 97 4.522 −2.569 8.345 Point 98 4.712 −2.478 8.357 Point 99 4.901 −2.383 8.369 Point 100 5.089 −2.286 8.381 Point 101 5.275 −2.187 8.393 Point 102 5.460 −2.087 8.406 Point 103 5.645 −1.984 8.419 Point 104 5.828 −1.880 8.432 Point 105 6.011 −1.774 8.445 Point 106 6.193 −1.667 8.458 Point 107 6.374 −1.560 8.472 Point 108 6.554 −1.451 8.485 Point 109 6.735 −1.341 8.499 Point 110 6.914 −1.230 8.513 Point 111 7.093 −1.119 8.527 Point 112 7.272 −1.006 8.541 Point 113 7.450 −0.894 8.555 Point 114 7.628 −0.781 8.569 Point 115 7.806 −0.667 8.584 Point 116 7.983 −0.553 8.598 Point 117 8.160 −0.438 8.612 Point 118 8.336 −0.323 8.627 Point 119 8.512 −0.206 8.641 Point 120 8.688 −0.090 8.656 Section 12 Point 1 8.937 0.111 9.689 Point 2 8.744 0.093 9.687 Point 3 8.548 −0.005 9.675 Point 4 8.350 −0.100 9.663 Point 5 8.152 −0.194 9.651 Point 6 7.952 −0.286 9.639 Point 7 7.752 −0.375 9.628 Point 8 7.550 −0.462 9.617 Point 9 7.348 −0.547 9.607 Point 10 7.145 −0.630 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−0.472 −0.683 9.590 Point 47 −0.666 −0.580 9.602 Point 48 −0.860 −0.478 9.615 Point 49 −1.056 −0.379 9.628 Point 50 −1.254 −0.285 9.639 Point 51 −1.457 −0.201 9.650 Point 52 −1.666 −0.132 9.659 Point 53 −1.881 −0.088 9.664 Point 54 −2.100 −0.081 9.665 Point 55 −2.314 −0.127 9.659 Point 56 −2.484 −0.260 9.643 Point 57 −2.581 −0.454 9.618 Point 58 −2.618 −0.669 9.591 Point 59 −2.607 −0.886 9.564 Point 60 −2.559 −1.099 9.537 Point 61 −2.484 −1.304 9.512 Point 62 −2.386 −1.499 9.487 Point 63 −2.271 −1.685 9.464 Point 64 −2.142 −1.861 9.442 Point 65 −2.000 −2.028 9.421 Point 66 −1.848 −2.185 9.401 Point 67 −1.688 −2.334 9.383 Point 68 −1.519 −2.474 9.365 Point 69 −1.343 −2.605 9.349 Point 70 −1.161 −2.727 9.333 Point 71 −0.973 −2.840 9.319 Point 72 −0.780 −2.944 9.306 Point 73 −0.582 −3.039 9.294 Point 74 −0.380 −3.124 9.283 Point 75 −0.174 −3.200 9.274 Point 76 0.036 −3.266 9.266 Point 77 0.248 −3.322 9.259 Point 78 0.463 −3.368 9.253 Point 79 0.679 −3.404 9.248 Point 80 0.898 −3.431 9.245 Point 81 1.117 −3.447 9.243 Point 82 1.337 −3.453 9.242 Point 83 1.556 −3.450 9.242 Point 84 1.776 −3.438 9.244 Point 85 1.994 −3.417 9.247 Point 86 2.212 −3.388 9.250 Point 87 2.429 −3.350 9.255 Point 88 2.644 −3.305 9.261 Point 89 2.857 −3.253 9.267 Point 90 3.069 −3.194 9.275 Point 91 3.279 −3.129 9.283 Point 92 3.487 −3.058 9.292 Point 93 3.693 −2.983 9.301 Point 94 3.897 −2.902 9.311 Point 95 4.099 −2.817 9.322 Point 96 4.300 −2.728 9.333 Point 97 4.499 −2.636 9.345 Point 98 4.697 −2.540 9.357 Point 99 4.893 −2.442 9.369 Point 100 5.087 −2.341 9.382 Point 101 5.281 −2.237 9.395 Point 102 5.473 −2.131 9.408 Point 103 5.664 −2.023 9.421 Point 104 5.854 −1.914 9.435 Point 105 6.043 −1.803 9.449 Point 106 6.232 −1.691 9.463 Point 107 6.420 −1.577 9.477 Point 108 6.607 −1.463 9.492 Point 109 6.793 −1.348 9.506 Point 110 6.979 −1.231 9.521 Point 111 7.165 −1.115 9.535 Point 112 7.350 −0.997 9.550 Point 113 7.535 −0.879 9.565 Point 114 7.720 −0.761 9.580 Point 115 7.904 −0.642 9.595 Point 116 8.088 −0.523 9.610 Point 117 8.272 −0.404 9.624 Point 118 8.456 −0.285 9.639 Point 119 8.640 −0.166 9.654 Point 120 8.824 −0.046 9.669

Referring to FIG. 7, the airfoil core 1330 having an airfoil-shaped cross section includes a leading edge 1350, a trailing edge 1352, a pressure side 1360, a suction side 1362, and a partition 1370 to define a cooling path along which cooling fluid flows. In addition to the airfoil core profile shape, the X, Y, and Z coordinates also define the partition profile 1370. For example, the partition profile 1370 may be configured for impingement tube insertability as well as casting producibility.

FIG. 8 is an outer envelope of a nominal profile of the airfoil core 1330 according to an exemplary embodiment. The X, Y, and Z values listed in Table 1 illustrate ideal point location for each point of each section of airfoil core 1330. However, there exist variations from the ideal point location attributed to manufacturing tolerances and the like which should be taken into account. Therefore, a design envelope is established which sets forth an acceptable outer boundary or distance from a nominal profile 1400 for each section. Accordingly, it is understood that each X, Y, and Z point may include a tolerance or +/− value. A tolerance 1410 may be, for example, +/−0.120 inches in the formation of airfoil core 1330. For example, the tolerance 1410 includes an upper limit 1420 defined as a 0.120-inch deviation from nominal profile 1400 and a lower limit 1425 defined as a −0.120-inch variation from nominal profile 1400. The design envelope or tolerance 1410 is robust such that these variations do not impair mechanical and aerodynamic performance of the turbine nozzle 1320.

While one or more exemplary embodiments have been described with reference to the accompanying drawings, it is to be understood by those skilled in the art that various modifications and changes in form and details can be made therein without departing from the spirit and scope as defined by the appended claims. Therefore, the description of the exemplary embodiments should be construed in a descriptive sense only and not to limit the scope of the claims, and many alternatives, modifications, and variations will be apparent to those skilled in the art. 

What is claimed is:
 1. A turbine nozzle comprising: an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections, and wherein the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.
 2. The turbine nozzle according to claim 1, wherein the airfoil core shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil core profile sections.
 3. The turbine nozzle according to claim 1, wherein the airfoil core includes a pressure side, a suction side, and a partition extending between the pressure side and the suction side to define a cooling path along which cooling fluid flows.
 4. The turbine nozzle according to claim 1, wherein the airfoil core includes a core shape for a second stage turbine nozzle.
 5. The turbine nozzle according to claim 1, further comprising a coating applied to the airfoil core shape, the coating having a thickness of less than or equal to 0.010 inches.
 6. A turbine comprising: a turbine nozzle extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle comprises an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections, and wherein the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.
 7. The turbine according to claim 6, wherein the airfoil core shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil core profile sections.
 8. The turbine according to claim 6, wherein the airfoil core includes a partition extending between the pressure side and the suction side to define a cooling path along which cooling fluid flows.
 9. The turbine according to claim 6, wherein the airfoil core includes a core shape for a second stage turbine nozzle.
 10. The turbine according to claim 6, further comprising a coating applied to the airfoil core shape, the coating having a thickness of less than or equal to 0.010 inches.
 11. A gas turbine comprising: a compressor configured to compress air; a combustor configured to mix compressed air supplied from the compressor with fuel for combustion to generate combustion gas; and a turbine comprising a plurality of turbine nozzles and a plurality of turbine blades rotated by the combustion gas to generate power, wherein each of the turbine nozzles extending from a platform to an end wall and having an airfoil-shaped cross section having a leading edge, a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle comprises an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections, and wherein the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.
 12. The gas turbine according to claim 11, wherein the airfoil core shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil core profile sections.
 13. The gas turbine according to claim 11, wherein the airfoil core includes a partition extending between the pressure side and the suction side to define a cooling path along which cooling fluid flows.
 14. The gas turbine according to claim 11, further comprising a coating applied to the airfoil core shape, the coating having a thickness of less than or equal to 0.010 inches. 